WP6发动机改RF031燃气轮机中低热值燃烧室改进设计  

Improved Design of Low/Middle Calorific Combustor for RF031 Gas Turbine Derived From WP6 Aeroengine

作　　者：冯大强[1] 杨灵[1] 屈成泽[1] 朱涛[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703

出　　处：《航空发动机》2010年第1期14-19,共6页Aeroengine

摘　　要：详细介绍了由WP6航空发动机去掉3级压气机改型而成的RF031燃气轮机燃烧室所用燃料由航空煤油改为中低热值气态燃料而进行的改进设计方案。经改进设计,实现了该燃烧室中低热值燃料(10467kJ/m3)的稳定燃烧,经试验验证,各项指标满足总体要求,基本实现了WP6发动机改地面燃气轮机的第1步目标。RF031 gas turbine is derived from WP6 by removing 3 stages compressor and changing fuel from kerosene to low/middle calorific fuel. The improved concept and validation results of improved combustor were presented based on WP6 combustor. The combustion stabilization was achieved with low/middle calorific fuel （10467kJ/m^3） The various performance of the combustor could basically meet the general requirements and the preliminary goal of the RF031.

关 键 词：燃烧室 中低热值 燃气轮机 改进设计 WP6发动机 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程] TK124[动力工程及工程热物理—工程热物理]